96-14869. Airworthiness Directives; Teledyne Continental Motors (formerly Bendix) S-20, S-1200, D-2000, and D-3000 Series Magnetos  

  • [Federal Register Volume 61, Number 115 (Thursday, June 13, 1996)]
    [Rules and Regulations]
    [Pages 29934-29936]
    From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
    [FR Doc No: 96-14869]
    
    
    
    -----------------------------------------------------------------------
    
    
    DEPARTMENT OF TRANSPORTATION
    14 CFR Part 39
    
    [Docket No. 93-ANE-07; Amendment 39-9649; AD 96-12-07]
    RIN 2120-AA64
    
    
    Airworthiness Directives; Teledyne Continental Motors (formerly 
    Bendix) S-20, S-1200, D-2000, and D-3000 Series Magnetos
    
    AGENCY: Federal Aviation Administration, DOT.
    
    ACTION: Final rule.
    
    -----------------------------------------------------------------------
    
    SUMMARY: This amendment supersedes an existing airworthiness directive 
    (AD), applicable to Teledyne Continental Motors (TCM) (formerly Bendix) 
    S-20, S-1200, D-2000, and D-3000 series magnetos equipped with impulse 
    couplings, that currently requires inspections for wear, and 
    replacement, if necessary, of the impulse coupling assemblies. This 
    amendment requires replacement, if necessary, of worn riveted impulse 
    coupling assemblies with serviceable riveted impulse couplings or snap 
    ring impulse couplings. This amendment is prompted by the availability 
    of an improved design for the impulse coupling assembly. The actions 
    specified by this AD are intended to prevent magneto failure and 
    subsequent engine failure.
    
    DATES: Effective July 18, 1996.
        The incorporation by reference of certain publications listed in 
    the regulations is approved by the Director of the Federal Register as 
    of July 18, 1996.
    
    ADDRESSES: The service information referenced in this AD may be 
    obtained from Teledyne Continental Motors, P.O. Box 90, Mobile, AL 
    36601; telephone (334) 438-3411. This information may be examined at 
    the Federal Aviation Administration (FAA), New England Region, Office 
    of the Assistant Chief Counsel, 12 New England Executive Park, 
    Burlington, MA 01803-5299; or at the Office of the Federal Register, 
    800 North Capitol Street, NW., suite 700, Washington, DC.
    
    FOR FURTHER INFORMATION CONTACT: Jerry Robinette, Aerospace Engineer, 
    Atlanta Certification Office, FAA, Small Airplane Directorate, Campus 
    Building, 1701 Columbia Avenue, Suite 2-160, College Park, GA, 30337-
    2748; telephone (404) 305-7371, fax (404) 305-7348.
    
    SUPPLEMENTARY INFORMATION: On January 4, 1983, the Federal Aviation 
    Administration (FAA) issued airworthiness directive (AD) 78-09-07 R3, 
    Amendment 39-4538 (48 FR 1482, January 13, 1983), to require 
    inspections for wear, and replacement, if necessary, of the impulse 
    coupling assemblies on certain Teledyne Continental Motors (TCM) 
    (formerly Bendix) S-20, S-1200, D-2000, and D-3000 series magnetos 
    equipped with impulse couplings. That action was prompted by reports of 
    numerous magneto failures. That condition, if not corrected, could 
    result in magneto failure and subsequent engine failure.
        A proposal to amend part 39 of the Federal Aviation Regulations was 
    published as a notice of proposed rulemaking (NPRM) in the Federal 
    Register on September 21, 1993 (58 FR 48987). That NPRM would have 
    retained the repetitive inspections for wear required by the current 
    AD, but would have also required replacement, if necessary, of the 
    riveted impulse coupling assembly with newly designed, improved, snap 
    ring impulse coupling assemblies. In addition, the proposed AD would 
    have required marking the magneto data plate to indicate installation 
    of a snap ring impulse coupling assembly. Installation of snap ring 
    impulse coupling assemblies would have constituted terminating action 
    to the inspection requirements of this AD. That NPRM was prompted by 
    the manufacturer redesigning the impulse coupling assembly to include 
    snap ring fastening technology which strengthens the cam axle and 
    reduces wear. The snap ring impulse coupling assembly was believed not 
    to have the failure mode of the previous design.
        Since the issuance of that NPRM, the FAA received reports of snap 
    ring impulse coupling assemblies being worn beyond limits. The FAA 
    determined that it was necessary to reopen the proposal for public 
    comment, so a Supplemental NPRM was published in the Federal Register 
    on November 17, 1994 (59 FR 59391). That Supplemental NPRM proposed to 
    retain the 500 hour repetitive inspections for wear required by the 
    current AD, but would require these inspections for
    
    [[Page 29935]]
    
    magnetos equipped with snap ring impulse coupling assemblies as well.
        Since the issuance of that Supplemental NPRM, the FAA received 
    comments that serviceable riveted impulse couplings should be permitted 
    as replacement units as well as the snap ring design. The FAA 
    concurred, since there has been no production of riveted impulse 
    couplings since January 1992, distributors still have some left as this 
    was a common, relatively high use item. The FAA determined that it was 
    necessary to reopen the proposal for public comment, so a Supplemental 
    NPRM was published in the Federal Register on October 16, 1995 (60 FR 
    53558). That Supplemental NPRM proposed to require replacement of worn 
    impulse couplings with serviceable impulse couplings of either riveted 
    or snap ring design.
        Interested persons have been afforded an opportunity to participate 
    in the making of this amendment. No comments were received since 
    publication of the last Supplemental NPRM.
        Since the issuance of that Supplemental NPRM, the manufacturer has 
    advised the FAA that the cost for replacement of the impulse coupling 
    assembly has increased from $125 to $140. The economic analysis of this 
    final rule has been revised accordingly.
        After careful review of the available data, the FAA has determined 
    that air safety and the public interest require the adoption of the 
    rule with the changes described previously. The FAA has determined that 
    these changes will not increase the scope of the AD.
        The FAA estimates that 130,000 magnetos installed on aircraft of 
    U.S. registry will be affected by this AD, that it will take 
    approximately 1 work hour, plus 1 work hour to change the impulse 
    coupling, and that the average labor rate is $60 per work hour. The 
    average utilization of the fleet of these airplanes is estimated to be 
    evenly divided between commercial/commuter service and private owners. 
    The commercial/commuter service population is estimated to operate 500 
    hours time in service (TIS) per year; therefore the cost to perform the 
    inspections required by the AD will be approximately $3,900,000 per 
    year. The FAA estimates that private owners operate their aircraft 
    between 50 and 100 hours TIS per year; therefore it will take 
    approximately 5 to 10 years to reach 500 hours time in service. The 
    estimated cost for these owners will also be $3,900,000 spread over a 
    time period of 5 to 10 years or 780,000 per year for 5 years or 
    $390,000 for 10 years. The cost to replace the impulse coupling 
    assembly is $140 per magneto plus one work hour at $60 per work hour 
    for a total of $200 per magneto. While all the riveted impulse coupling 
    assemblies will eventually have to be replaced, it is not possible to 
    estimate the cost per year. The total cost for replacement for U.S. 
    operators is estimated to be $26,000,000.
        The regulations adopted herein will not have substantial direct 
    effects on the States, on the relationship between the national 
    government and the States, or on the distribution of power and 
    responsibilities among the various levels of government. Therefore, in 
    accordance with Executive Order 12612, it is determined that this final 
    rule does not have sufficient federalism implications to warrant the 
    preparation of a Federalism Assessment.
        For the reasons discussed above, I certify that this action (1) is 
    not a ``significant regulatory action'' under Executive Order 12866; 
    (2) is not a ``significant rule'' under DOT Regulatory Policies and 
    Procedures (44 FR 11034, February 26, 1979); and (3) will not have a 
    significant economic impact, positive or negative, on a substantial 
    number of small entities under the criteria of the Regulatory 
    Flexibility Act. A final evaluation has been prepared for this action 
    and it is contained in the Rules Docket. A copy of it may be obtained 
    from the Rules Docket at the location provided under the caption 
    ADDRESSES.
    
    List of Subjects in 14 CFR Part 39
    
        Air Transportation, Aircraft, Aviation safety, Incorporation by 
    reference, Safety.
    
    Adoption of the Amendment
    
        Accordingly, pursuant to the authority delegated to me by the 
    Administrator, the Federal Aviation Administration amends part 39 of 
    the Federal Aviation Regulations (14 CFR part 39) as follows:
    
    PART 39--AIRWORTHINESS DIRECTIVES
    
        1. The authority citation for part 39 continues to read as follows:
    
        Authority: 49 U.S.C. 106(g), 40113, 44701.
    
    
    Sec. 39.13    [Amended]
    
        2. Section 39.13 is amended by removing Amendment 39-4538 (48 FR 
    1482, January 13, 1983) and by adding a new airworthiness directive, 
    Amendment 39-9649, to read as follows:
    
    96-12-07  Teledyne Continental Motors: Amendment 39-9649. Docket 93-
    ANE-07. Supersedes AD 78-09-07 R3, Amendment 39-4538.
    
        Applicability: Teledyne Continental Motors (TCM) (formerly 
    Bendix) S-20, S-1200, D-2000, and D-3000 series magnetos equipped 
    with impulse couplings, installed on but not limited to 
    reciprocating engine powered aircraft manufactured by Beech, Cessna, 
    Mooney, and Piper.
    
        Note 1: This airworthiness directive (AD) applies to each 
    magneto identified in the preceding applicability provision, 
    regardless of whether it has been modified, altered, or repaired in 
    the area subject to the requirements of this AD. For magnetos that 
    have been modified, altered, or repaired so that the performance of 
    the requirements of this AD is affected, the owner/operator must use 
    the authority provided in paragraph (c) to request approval from the 
    Federal Aviation Administration (FAA). This approval may address 
    either no action, if the current configuration eliminates the unsafe 
    condition, or different actions necessary to address the unsafe 
    condition described in this AD. Such a request should include an 
    assessment of the effect of the changed configuration on the unsafe 
    condition addressed by this AD. In no case does the presence of any 
    modification, alteration, or repair remove any magneto from the 
    applicability of this AD.
    
        Note 2: The FAA has received reports of some confusion as to 
    what is meant by S-20, S-1200, D-2000, and D-3000 series magnetos as 
    referenced in TCM Mandatory Service Bulletin (MSB) No. MSB645, dated 
    April 4, 1994, and this airworthiness directive (AD). A typical 
    example is S6RN-25, where the S designates single type ignition unit 
    (a D designates a dual ignition unit), the 6 designates the number 
    of cylinders, the R designates right hand rotation, the N is the 
    manufacturer designation (this did not change when TCM purchased the 
    Bendix magneto product line), and the number after the dash 
    indicates the series (a -25 is a S-20 series magneto while a -3200 
    is a D-3000 series magneto, etc.).
    
        Compliance: Required as indicated, unless accomplished 
    previously.
        To prevent magneto failure and subsequent engine failure, 
    accomplish the following:
        (a) For magnetos with riveted or snap ring impulse coupling 
    assemblies, having less than 450 hours time in service (TIS) since 
    new, or overhaul, or since last inspection, on the effective date of 
    this AD, accomplish the following:
        (1) Prior to the accumulation of 500 hours TIS since new, or 
    overhaul, or since last inspection, inspect riveted or snap ring 
    impulse coupling assemblies for wear, and replace, if necessary, 
    prior to further flight, with serviceable riveted or snap ring 
    impulse coupling assemblies, in accordance with the Detailed 
    Instructions of TCM MSB No. MSB645, dated April 4, 1994, and TCM SB 
    No. 639, dated March 1993.
        (2) Thereafter, at intervals not to exceed 500 hours TIS since 
    the last inspection, 
    
    [[Page 29936]]
    
    inspect riveted or snap ring impulse coupling assemblies for wear, and 
    replace, if necessary, prior to further flight, with serviceable 
    riveted or snap ring impulse coupling assemblies, in accordance with 
    the Detailed Instructions of TCM MSB No. MSB645, dated April 4, 1994, 
    and TCM SB No. 639, dated March 1993.
        (b) For magnetos with riveted or snap ring impulse coupling 
    assemblies, having 450 or more hours TIS since new, or overhaul, or 
    since last inspection, on the effective date of this AD, or an 
    unknown TIS on the effective date of this AD, accomplish the 
    following:
        (1) Within the next 50 hours TIS after the effective date of 
    this AD, inspect riveted or snap ring impulse coupling assemblies 
    for wear, and replace, if necessary, prior to further flight, with 
    serviceable riveted or snap ring impulse coupling assemblies in 
    accordance with the Detailed Instructions of TCM MSB No. MSB645, 
    dated April 4, 1994, and TCM SB No. 639, dated March 1993.
        (2) Thereafter, at intervals not to exceed 500 hours TIS since 
    the last inspection, inspect riveted or snap ring impulse coupling 
    assemblies for wear, and replace, if necessary, prior to further 
    flight, with serviceable riveted or snap ring impulse coupling 
    assemblies, in accordance with the Detailed Instruction of TCM MSB 
    No. MSB645, dated April 4, 1994, and TCM SB No. 639, dated March 
    1993.
        (c) An alternative method of compliance or adjustment of the 
    compliance time that provides an acceptable level of safety may be 
    used if approved by the Manager, Atlanta Aircraft Certification 
    Office. The request should be forwarded through an appropriate FAA 
    Maintenance Inspector, who may add comments and then send it to the 
    Manager, Atlanta Aircraft Certification Office.
    
        Note: Information concerning the existence of approved 
    alternative methods of compliance with this airworthiness directive, 
    if any, may be obtained from the Atlanta Aircraft Certification 
    Office.
    
        (d) Special flight permits may be issued in accordance with 
    sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
    CFR 21.197 and 21.199) to operate the aircraft to a location where 
    the requirements of this AD can be accomplished.
        (e) The actions required by this AD shall be done in accordance 
    with the following TCM service documents:
    
    ------------------------------------------------------------------------
             Document No.            Pages       Revision          Date     
    ------------------------------------------------------------------------
    MSB No. MSB645................      1-6  Original.......  Apr. 4, 1994. 
      Total Pages: 6                                                        
    SB No. 639....................      1-2  Original.......  Mar. 1993.    
      Total Pages: 2                                                        
    ------------------------------------------------------------------------
    
    This incorporation by reference was approved by the Director of the 
    Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
    51. Copies may be obtained from Teledyne Continental Motors, P.O. 
    Box 90, Mobile, AL 36601; telephone (334) 438-3411. Copies may be 
    inspected at the FAA, New England Region, Office of the Assistant 
    Chief Counsel, 12 New England Executive Park, Burlington, MA; or at 
    the Office of the Federal Register, 800 North Capitol Street, NW., 
    suite 700, Washington, DC.
        (f) This amendment becomes effective on July 18, 1996.
    
        Issued in Burlington, Massachusetts, on May 29, 1996.
    Robert E. Guyotte,
    Acting Manager, Engine and Propeller Directorate, Aircraft 
    Certification Service.
    [FR Doc. 96-14869 Filed 6-12-96; 8:45 am]
    BILLING CODE 4910-13-U
    
    

Document Information

Effective Date:
7/18/1996
Published:
06/13/1996
Department:
Transportation Department
Entry Type:
Rule
Action:
Final rule.
Document Number:
96-14869
Dates:
Effective July 18, 1996.
Pages:
29934-29936 (3 pages)
Docket Numbers:
Docket No. 93-ANE-07, Amendment 39-9649, AD 96-12-07
RINs:
2120-AA64: Airworthiness Directives
RIN Links:
https://www.federalregister.gov/regulations/2120-AA64/airworthiness-directives
PDF File:
96-14869.pdf
CFR: (1)
14 CFR 39.13